Hydrogen-exhaust gas heat exchanger of a turbofan engine

ABSTRACT

A turbofan engine includes a fan, a core turbine engine having one or more turbines and an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and a number of turbine stages of the turbofan engine. The load capacity factor is between 4.37 and 28.65 for the fan diameter being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m 2 /m 3  and 10,000 m 2 /m 3 .

FIELD

The present disclosure relates to a hydrogen-exhaust gas heat exchangerfor a turbofan engine.

BACKGROUND

Recently, there has been a push toward developing hydrogen-poweredturbofan engines for aircraft, or rather, turbofan engines that utilizehydrogen as the fuel source. In some instances, hydrogen can be storedas a liquid in one or more tanks at cryogenic temperatures, such as atnegative two hundred fifty degrees Celsius (−250° C.). Deliveringhydrogen from the one or more tanks for combustion may present certainchallenges.

BRIEF DESCRIPTION OF THE DRAWINGS

A full and enabling disclosure of the present disclosure, including thebest mode thereof, directed to one of ordinary skill in the art, is setforth in the specification, which makes reference to the appendedfigures, in which:

FIG. 1 provides a schematic cross-sectional view of a turbofan engine inaccordance with an example embodiment of the present disclosure;

FIG. 2 provides a schematic diagram of a hydrogen delivery systemassociated with the turbofan engine of FIG. 1 ;

FIG. 3 provides a perspective view of a hydrogen-exhaust gas heatexchanger of the turbofan engine of FIG. 1 ;

FIG. 4 provides a perspective view of an exchanger unit of thehydrogen-exhaust gas heat exchanger of FIG. 3 ;

FIG. 5 provides a cross-sectional view of a core of the exchanger unittaken along line 5-5 of FIG. 4 ;

FIG. 6 lists various relationships between hydrogen-exhaust gas heatexchanger characteristics and operational and architecturalcharacteristics of a turbofan engine in accordance with an exampleembodiment of the present disclosure;

FIGS. 7 through 13 each graphically depict a load capacity factor of ahydrogen-exhaust gas heat exchanger of a turbofan engine as a functionof a fan diameter of a fan of the turbofan engine in accordance withexample embodiments of the present disclosure;

FIG. 14 provides a table listing values for different example turbofanengines in accordance with example embodiments of the presentdisclosure; and

FIG. 15 provides a flow diagram for a method of operating a turbofanengine having a hydrogen-exhaust gas heat exchanger in accordance withan example embodiment of the present disclosure.

DETAILED DESCRIPTION

Reference will now be made in detail to present embodiments of thedisclosure, one or more examples of which are illustrated in theaccompanying drawings. The detailed description uses numerical andletter designations to refer to features in the drawings. Like orsimilar designations in the drawings and description have been used torefer to like or similar parts of the disclosure.

As used herein, the terms “first”, “second”, and “third” may be usedinterchangeably to distinguish one component from another and are notintended to signify location or importance of the individual components.

The terms “coupled,” “fixed,” “attached to,” and the like refer to bothdirect coupling, fixing, or attaching, as well as indirect coupling,fixing, or attaching through one or more intermediate components orfeatures, unless otherwise specified herein.

The singular forms “a”, “an”, and “the” include plural references unlessthe context clearly dictates otherwise.

The term “at least one of” in the context of, e.g., “at least one of A,B, and C” refers only A, only B, only C, or any combination of A, B, andC.

Here and throughout the specification and claims, range limitations arecombined and interchanged, such ranges are identified and include allthe sub-ranges contained therein unless context or language indicatesotherwise. For example, all ranges disclosed herein are inclusive of theendpoints, and the endpoints are independently combinable with eachother.

In an effort to further curb or eliminate carbon emissions, enginedesigners have recently pushed toward hydrogen-powered turbofan enginesfor aircraft, or rather, turbofan engines that utilize hydrogen as afuel source for combustion. Hydrogen, the most abundant element in theuniverse, produces no carbon dioxide emissions when burned. Despite thebenefits of using hydrogen over conventional fossil fuel sources, thereare certain challenges associated with using hydrogen as the fuel sourcefor turbofan engines. For instance, the inventors of the presentdisclosure have recognized that increasing a temperature of hydrogen,which is commonly stored as a liquid at cryogenic temperatures, to atemperature more suitable for combustion presents certain challenges.Pre-heating hydrogen to the needed combustion temperature for combustionmay facilitate better fuel efficiency.

The inventors of the present disclosure developed architectures for aturbofan engine having a hydrogen-exhaust gas heat exchanger operable tofacilitate heat exchange between hydrogen being delivered for combustionand exhaust gas produced by the turbofan engine. Particularly, theinventors proceeded in the manner of designing turbofan engines withgiven fan characteristics, turbomachine characteristics (e.g., number ofturbine stages), and hydrogen-exhaust gas heat exchangercharacteristics; checking the potential of the hydrogen-exhaust gas heatexchanger to process the heat duty of hydrogen being delivered forcombustion; redesigning the turbofan engine and/or the hydrogen-exhaustgas heat exchanger by varying the fan, turbomachine characteristics(e.g., the number of turbine stages), and/or hydrogen-exhaust gas heatexchanger characteristics; and rechecking the potential of thehydrogen-exhaust gas heat exchanger to process the heat duty of hydrogenbeing delivered for combustion of the redesigned turbofan engine and/orhydrogen-exhaust gas heat exchanger during the design of severaldifferent types of turbofan engines, including the gas turbine enginedescribed below with reference to FIG. 1 .

During the course of this practice of studying/evaluating various fancharacteristics, turbomachine characteristics (e.g., number of turbinestages), and hydrogen-exhaust gas heat exchanger characteristicsconsidered feasible for best satisfying mission requirements, theinventors unexpectedly discovered that a certain relationship existsbetween a compactness of the hydrogen-exhaust gas heat exchanger and aflow potential of the process fluid, or exhaust gas in this instance.The relationship between the compactness of the hydrogen-exhaust gasheat exchanger and the flow potential of the process fluid is capturedby a load capacity factor. The load capacity factor can be thought of asan indicator of the compactness and effectiveness of a hydrogen-exhaustgas heat exchanger to process the heat duty of hydrogen being deliveredfor combustion given the architectural arrangement of the turbofanengine and the hydrogen-exhaust gas heat exchanger, and in addition, anindication of an improvement in the turbofan and/or hydrogen-exhaust gasheat exchanger packaging, weight, and ability to pre-heat hydrogen tothe needed combustion temperature for combustion.

Referring now to the drawings, FIG. 1 provides a schematiccross-sectional view of a turbofan engine 100 according to an exampleembodiment of the present disclosure. For the depicted embodiment ofFIG. 1 , the turbofan engine 100 is an aeronautical, high-bypassturbofan engine configured to be mounted to an aircraft, e.g., in anunder-wing configuration. As shown, the turbofan engine 100 defines anaxial direction A, a radial direction R, and a circumferential directionC. The axial direction A extends parallel to or coaxial with alongitudinal centerline 102 defined by the turbofan engine 100.

The turbofan engine 100 includes a fan section 104 and a core turbineengine 106 disposed downstream of the fan section 104. The core turbineengine 106 includes an engine cowl 108 that defines an annular coreinlet 110. The engine cowl 108 encases, in a serial flow relationship, acompressor section 112 including a first, booster or LP compressor 114and a second, HP compressor 116; a combustion section 118; a turbinesection 120 including a first, HP turbine 122 and a second, LP turbine124; and an exhaust section 126. The compressor section 112, combustionsection 118, turbine section 120, and exhaust section 126 togetherdefine a core air flowpath 132 through the core turbine engine 106.

An HP shaft 128 drivingly connects the HP turbine 122 to the HPcompressor 116. An LP shaft 130 drivingly connects the LP turbine 124 tothe LP compressor 114. The HP shaft 128, the rotating components of theHP compressor 116 that are mechanically coupled with the HP shaft 128,and the rotating components of the HP turbine 122 that are mechanicallycoupled with the HP shaft 128 collectively form a high pressure spool,or HP spool 131. The LP shaft 130, the rotating components of the LPcompressor 114 that are mechanically coupled with the LP shaft 130, andthe rotating components of the LP turbine 124 that are mechanicallycoupled with the LP shaft 130 collectively form a low pressure spool, orLP spool 133.

The fan section 104 includes a fan assembly 138 having a fan 134mechanically coupled with a fan rotor 140. The fan 134 has a pluralityof fan blades 136 circumferentially-spaced apart from one another. Asdepicted, the fan blades 136 extend outward from the fan rotor 140generally along the radial direction R. A power gearbox 142 mechanicallycouples the LP spool 133 and the fan rotor 140. The power gearbox 142may also be called a main gearbox. The power gearbox 142 includes aplurality of gears for stepping down the rotational speed of the LPshaft 130 to provide a more efficient rotational fan speed of the fan134. In other example embodiments, the fan blades 136 of the fan 134 canbe mechanically coupled with a suitable actuation member configured topitch the fan blades 136 about respective pitch axes, e.g., in unison.In some alternative embodiments, the turbofan engine 100 does notinclude the power gearbox 142. In such alternative embodiments, the fan134 can be directly mechanically coupled with the LP shaft 130, e.g., ina direct drive configuration.

Referring still to FIG. 1 , the fan rotor 140 and hubs of the fan blades136 are covered by a rotatable spinner 144 aerodynamically contoured topromote an airflow through the plurality of fan blades 136.Additionally, the fan section 104 includes an annular fan casing orouter nacelle 146 that circumferentially surrounds the fan 134 and/or atleast a portion of the core turbine engine 106. The nacelle 146 issupported relative to the core turbine engine 106 by a plurality ofcircumferentially-spaced outlet guide vanes 148. A downstream section150 of the nacelle 146 extends over an outer portion of the core turbineengine 106 so as to define a bypass passage 152 therebetween.

During operation of the turbofan engine 100, a volume of air 154 entersthe turbofan engine 100 through an associated inlet 156 of the nacelle146 and/or fan section 104. As the volume of air 154 passes across thefan blades 136, a first portion of air 158 is directed or routed intothe bypass passage 152 and a second portion of air 160 is directed orrouted into the core inlet 110. The pressure of the second portion ofair 160 is progressively increased as it flows downstream through the LPcompressor 114 and HP compressor 116. Particularly, the LP compressor114 includes sequential stages of LP compressor stator vanes 182 and LPcompressor blades 184 that progressively compress the second portion ofair 160. The LP compressor blades 184 are mechanically coupled to the LPshaft 130. Similarly, the HP compressor 116 includes sequential stagesof HP compressor stator vanes 186 and HP compressor blades 188 thatprogressively compress the second portion of air 160 even further. TheHP compressor blades 188 are mechanically coupled to the HP shaft 128.The compressed second portion of air 160 is then discharged from thecompressor section 112 into the combustion section 118.

The compressed second portion of air 160 discharged from the compressorsection 112 mixes with fuel and is burned within a combustor of thecombustion section 118 to provide combustion gases 162. The combustiongases 162 are routed from the combustion section 118 along a hot gaspath 174 of the core air flowpath 132 through the HP turbine 122 where aportion of thermal and/or kinetic energy from the combustion gases 162is extracted via sequential stages of HP turbine stator vanes 164 and HPturbine blades 166. The HP turbine blades 166 are mechanically coupledto the HP shaft 128. Thus, when the HP turbine blades 166 extract energyfrom the combustion gases 162, the HP shaft 128 rotates, therebysupporting operation of the HP compressor 116. The combustion gases 162are routed through the LP turbine 124 where a second portion of thermaland kinetic energy is extracted from the combustion gases 162 viasequential stages of LP turbine stator vanes 168 and LP turbine blades170. The LP turbine blades 170 are coupled to the LP shaft 130. Thus,when the LP turbine blades 170 extract energy from the combustion gases162, the LP shaft 130 rotates, thereby supporting operation of the LPcompressor 114, as well as the fan 134 by way of the power gearbox 142.

The combustion gases 162 exit the LP turbine 124 and are exhausted fromthe core turbine engine 106 as exhaust gases or exhaust gas 163. Asshown in FIG. 1 , the exhaust gas 163 is routed through the exhaustsection 126 of the core turbine engine 106 and exhausted therefrom toprovide propulsive thrust. Simultaneously, the pressure of the firstportion of air 158 is substantially increased as the first portion ofair 158 is routed through the bypass passage 152 before the firstportion of air 158 is exhausted from a fan nozzle exhaust section 172 ofthe turbofan engine 100, also providing propulsive thrust. The HPturbine 122, the LP turbine 124, and the exhaust section 126 at leastpartially define the hot gas path 174.

As further shown in FIG. 1 , the turbofan engine 100 includes a hydrogendelivery system 190 for delivering hydrogen H2 to the combustion section118 for combustion. In this regard, the power source for the turbofanengine 100 of FIG. 1 is hydrogen fuel. The hydrogen delivery system 190includes a hydrogen supply line 192 that provides flow communicationbetween one or more hydrogen tanks 194 (FIG. 2 ) and the combustionsection 118. Hydrogen can be stored in a liquid state in the one or morehydrogen tanks 194 at low temperatures, such as at negative two hundredfifty degrees Celsius (−250° C.). Alternatively, hydrogen can be storedin a gaseous state in the one or more hydrogen tanks 194 at highpressure. The one or more hydrogen tanks 194 can be stored onboard afuselage of the aircraft to which the turbofan engine 100 is mounted,for example. To achieve better fuel efficiency, the hydrogen deliverysystem 190 includes one or more heat exchangers to pre-heat the hydrogenfuel so that the hydrogen fuel delivered to the combustion section 118is, or within a predetermined range of, a predetermined pre-combustiontemperature.

Particularly, with reference now to FIGS. 1 and 2 , FIG. 2 provides aschematic diagram of the hydrogen delivery system 190. As depicted, thehydrogen delivery system 190 includes a first heat exchanger 196positioned along the hydrogen supply line 192. The first heat exchanger196 is arranged so that a first fluid F1 imparts thermal energy tohydrogen H2 flowing along the hydrogen supply line 192. In this exampleembodiment, the first heat exchanger 196 is a hydrogen-to-oil heatexchanger. Accordingly, the first fluid F1 is oil.

The hydrogen delivery system 190 also includes a second heat exchanger198 positioned along the hydrogen supply line 192 downstream of thefirst heat exchanger 196. The second heat exchanger 198 is arranged sothat a second fluid F2 imparts thermal energy to the hydrogen H2 flowingalong the hydrogen supply line 192. In this example embodiment, thesecond heat exchanger 198 is a hydrogen-to-air heat exchanger.Accordingly, the second fluid F2 is air. The second fluid F2, or air,can be air bled from the core air flowpath 132, e.g., from a station ofthe turbofan engine 100 between the LP compressor 114 and the HPcompressor 116, from a stage of the HP compressor 116, etc.Alternatively, the second fluid F2, or air, can be air bled from thebypass passage 152.

The hydrogen delivery system 190 further includes a third heatexchanger, or hydrogen-exhaust gas heat exchanger 200. Thehydrogen-exhaust gas heat exchanger 200 is positioned along the hydrogensupply line 192 downstream of the second heat exchanger 198 and upstreamof the combustion section 118. As shown in FIG. 1 , the hydrogen-exhaustgas heat exchanger 200 can be positioned inward of the core air flowpath132 along the radial direction R. The hydrogen-exhaust gas heatexchanger 200 is arranged so that a third fluid F3, or exhaust gas 163from the exhaust section 126 of the core air flowpath 132 in thisexample embodiment, imparts thermal energy to the hydrogen H2 flowingalong the hydrogen supply line 192. In this regard, the hydrogen-exhaustgas heat exchanger 200 is a hydrogen-to-exhaust gas heat exchanger. Thehydrogen-exhaust gas heat exchanger 200 can receive the hydrogen H2 asliquid hydrogen, gaseous hydrogen, or in vapor form.

The first heat exchanger 196, the second heat exchanger 198, and thehydrogen-exhaust gas heat exchanger 200 process a heat duty of thehydrogen H2 flowing along the hydrogen supply line 192 so that hydrogenH2 delivered to the combustion section 118, is or within a predeterminedrange of, a predetermined pre-combustion temperature. In some exampleembodiments, the first heat exchanger 196 is configured to processbetween thirty and forty percent (30-40%) of the heat duty, the secondheat exchanger 198 is configured to process between twenty and fortypercent (20-40%) of the heat duty, and the hydrogen-exhaust gas heatexchanger 200 is configured to process between thirty and fifty percent(30-50%) of the heat duty of the hydrogen H2 to raise the hydrogen H2 toor within a predetermined range of the predetermined pre-combustiontemperature prior to be being delivered to a combustor of the combustionsection 118. As one example, the first heat exchanger 196 is configuredto process between thirty percent (30%) of the heat duty, the secondheat exchanger 198 is configured to process twenty percent (20%) of theheat duty, and the hydrogen-exhaust gas heat exchanger 200 is configuredto process fifty percent (50%) of the heat duty of the hydrogen H2 toraise the hydrogen H2 to or within a predetermined range of thepredetermined pre-combustion temperature.

In other example embodiments, the first heat exchanger 196 is configuredto process between thirty and forty percent (30-40%) of the heat duty,the second heat exchanger 198 is configured to process between thirtyand forty percent (30-40%) of the heat duty, and the hydrogen-exhaustgas heat exchanger 200 is configured to process between thirty and fortypercent (30-40%) of the heat duty of the hydrogen H2 to raise thehydrogen H2 to or within a predetermined range of the predeterminedpre-combustion temperature prior to be being delivered to a combustor ofthe combustion section 118. As one example, the first heat exchanger 196is configured to process thirty-three percent (33%) of the heat duty,the second heat exchanger 198 is configured to process thirty percent(30%) of the heat duty, and the hydrogen-exhaust gas heat exchanger 200is configured to process thirty-seven percent (37%) of the heat duty ofthe hydrogen H2 to raise the hydrogen H2 to or within a predeterminedrange of the predetermined pre-combustion temperature.

It will be appreciated that the turbofan engine 100 depicted in FIG. 1is provided by way of example only, and that in other exampleembodiments, the turbofan engine 100 may have any other suitableconfiguration. Additionally, or alternatively, aspects of the presentdisclosure may be utilized with any other suitable aeronautical turbofanengine, such as a turboshaft engine, turboprop engine, turbojet engine,etc.

FIG. 3 provides a perspective view of one example configuration of thehydrogen-exhaust gas heat exchanger 200 of FIGS. 1 and 2 . The firstheat exchanger 196 and the second heat exchanger 198 of FIGS. 1 and 2may be configured in a same or similar manner as the hydrogen-exhaustgas heat exchanger 200. For instance, the first and second heatexchangers 196, 198 may each include a plurality of exchanger units eachhaving a core defining first and second channels, as provided below.

As depicted in FIG. 3 , the hydrogen-exhaust gas heat exchanger 200defines a vertical direction V, a lateral direction L, and a transversedirection T that are orthogonal to one another. The hydrogen-exhaust gasheat exchanger 200 includes a plurality of exchanger units 210. Theexchanger units 210 can be compactly arranged in any suitableconfiguration. For this embodiment, the hydrogen-exhaust gas heatexchanger 200 includes twenty (20) exchanger units 210, including tenright-side exchanger units 211-220 stacked on top of one another alongthe vertical direction V and ten left-side exchanger units 221-230stacked on top of one another along the vertical direction V. Althoughthe hydrogen-exhaust gas heat exchanger 200 of FIG. 3 has twentyexchanger units 210, in other example embodiments, the hydrogen-exhaustgas heat exchanger 200 can include any suitable number of exchangerunits, such as one exchanger unit, eight exchanger units, fiftyexchanger units, etc. Further, in other embodiments, the exchanger units210 can be positioned side-by-side rather than stacked on one another.

With reference now to FIGS. 3, 4, and 5 , FIG. 4 provides a perspectiveview of a first exchanger unit 211 of the hydrogen-exhaust gas heatexchanger 200 of FIG. 3 . FIG. 5 provides a cross-sectional view of acore of the first exchanger unit 211 taken along line 5-5 of FIG. 4 .Generally, each exchanger unit 210 of the hydrogen-exhaust gas heatexchanger 200 has a core and two manifolds. The core of each exchangerunit defines first channels and second channels. The first channels canreceive a fluid, such as hydrogen, and the second channels can receive afluid, such as exhaust gas. The core of one or more of the exchangerunits 210 can be formed by a plurality of unit cells arranged in flowcommunication with one another. Alternatively, the core of one or moreof the exchanger units 210 can be formed as monolithic blocks.

By way of example, as depicted, the hydrogen-exhaust gas heat exchanger200 includes a core 240 defining first channels 241 (outlined by dashedlines in FIG. 5 ) and second channels 242 (outlined by solid lines inFIG. 5 ). The first channels 241 can receive hydrogen H2 and the secondchannels 242 can receive the third fluid F3, which is exhaust gas 163 inthis example. The third fluid F3 or exhaust gas 163 flowing through thesecond channels 242 can be warmer than the hydrogen H2 flowing throughthe first channels 241. In this way, thermal energy can be exchangedbetween the third fluid F3 or exhaust gas 163 and the hydrogen H2 asthey flow through the first exchanger unit 211. For this embodiment, thehydrogen H2 flowing through the first channels 241 (out of the page asrepresented by the “circled dot” in FIG. 5 ) is in crossflow directionwith respect to the third fluid F3 or exhaust gas 163 flowing throughthe second channels 242 (into the page as represented by the “circled X”in FIG. 5 ).

Although the core 240 of the first exchanger unit 211 is shown in astraight channel configuration in FIG. 4 , the core 240 of the firstexchanger unit 211 (as well as the cores of the other exchanger units210) can have other suitable configurations, such as a double U-bendchannel configuration, a single U-bend configuration, etc.

The first exchanger unit 211 includes a first manifold 244 and a secondmanifold 246. Generally, the first manifold 244 distributes the thirdfluid F3 or exhaust gas 163 to the second channels 242 and receives thehydrogen H2 from the first channels 241. The first manifold 244 can bearranged to keep the hydrogen H2 and the third fluid F3 or exhaust gas163 fluidly separate. Similarly, the second manifold 246 distributes thehydrogen H2 to the first channels 241 and receives the third fluid F3from the second channels 242. The second manifold 246 can be arranged tokeep the hydrogen H2 and the third fluid F3 fluidly separate. The firstmanifold 244 and/or second manifold 246 can be in flow communicationwith a manifold of an adjacent exchanger unit such that the hydrogen H2and/or the third fluid F3 can flow between exchanger units 210 of thehydrogen-exhaust gas heat exchanger 200.

Each exchanger unit 210 of the hydrogen-exhaust gas heat exchanger 200can be configured in a same or similar manner as the first exchangerunit 211 provided above. In this way, each exchanger unit 210 of thehydrogen-exhaust gas heat exchanger 200 can have a core arranged in asame or similar manner as the core 240 of the first exchanger unit 211and two manifolds arranged in a same or similar manner as the first andsecond manifolds 244, 246 of the first exchanger unit 211. The core ofeach exchanger unit 210 defines first channels and second channels justas the core 240 defines the defines the first channels 241 and thesecond channels 242.

As alluded to earlier, the inventors discovered, unexpectedly during thecourse of engine design, that a relationship exists between thecompactness of a hydrogen-exhaust gas heat exchanger, as represented bya heat transfer surface area density, and the flow potential of exhaustgas to process the heat duty of hydrogen, as represented by a processconductance parameter. The process conductance parameter relates anexhaust gas temperature at takeoff, an ambient air temperature attakeoff, a critical temperature of hydrogen, an exhaust gas massflowrate at takeoff, a mass flowrate factor of hydrogen at criticalcondition, a fan diameter of the fan, and a number of turbine stages ofone or more turbines of a turbofan engine. The relationship between thecompactness of a hydrogen-exhaust gas heat exchanger and a flowpotential of exhaust gas to process the heat duty of hydrogen isrepresented by a load capacity factor. The inventors found that ahydrogen-exhaust gas heat exchanger having a load capacity factor withinone of the ranges specified herein provides a hydrogen-exhaust gas heatexchanger that is both compact and effective at processing the heat dutyassociated with hydrogen being delivered for combustion given the flowpotential of the exhaust gas produced by the turbofan engine.

The ranges of load capacity factors noted below represent examples ofengine designs utilizing hydrogen-exhaust gas heat exchangers that takeinto consideration the various benefits and penalties of choosing onestructural architecture of one hydrogen-exhaust gas heat exchangerand/or turbofan engine over another. In this regard, as discovered bythe inventors, the ranges of load capacity factors provided hereinstrike a balance between the compactness and weight of ahydrogen-exhaust gas heat exchanger, the ability of the hydrogen-exhaustgas heat exchanger to process the heat duty of hydrogen being deliveredfor combustion, the susceptibility of the channels of thehydrogen-exhaust gas heat exchanger becoming blocked or contaminated,the manufacturability of the hydrogen-exhaust gas heat exchanger, themanufacturability of the turbofan engine, and the impact that the numberof turbine stages has on the exhaust gas exiting the turbofan engine aswell as the thrust output of the turbofan engine.

In addition to discovering the load capacity factor, the inventorsdiscovered that a relationship exists between the load capacity factorassociated with a hydrogen-exhaust gas heat exchanger and a fan diameterof a fan of a turbofan engine. The inventors observed that the loadcapacity factor increases exponentially the larger the fan diameter of agiven turbofan engine. That is, the inventors observed that, as fandiameter increases, flow potential of exhaust gas to thehydrogen-exhaust gas exchanger increases (as represented by theincreasing load capacity factor). This discovered relationship can beused advantageously to design hydrogen-powered turbofan engines andtheir associated hydrogen-exhaust gas heat exchangers.

Further, utilizing the load capacity factor, the inventors found thatthe number of suitable or feasible engine and/or hydrogen-exhaust gasheat exchanger designs that allow a hydrogen-exhaust gas heat exchangerto meet compactness, weight, and heat duty requirements could be greatlydiminished, which can facilitate a more rapid down selection of designsto consider as a turbofan engine having a hydrogen-exhaust gas heatexchanger is developed. Such a benefit provides more insight into therequirements for a given turbofan engine well before specifictechnologies, integration, and system requirements are developed fully.It may also prevent late-stage redesign. For instance, selection of ahydrogen-exhaust gas heat exchanger's heat transfer surface area densitymay be facilitated by utilizing a load capacity factor within the rangesprovided herein, which may help determine the needed channel diametersand wall thickness of the core of the hydrogen-exhaust gas heatexchanger. Moreover, utilizing a load capacity factor within the rangesprovided herein may eliminate or otherwise reduce implementation of heatexchangers having heat transfer surface area density values that are toohigh, making them not practical to manufacture. Higher heat transfersurface area density values may create higher susceptibility toblocking/contamination of the exchanger channels, which may limit theheat exchanger's effectiveness. Also, utilizing a load capacity factorwithin the ranges provided herein may facilitate exclusion or reductionof hydrogen-exhaust gas heat exchangers that are bulky.

With reference now to FIGS. 1, 2, 3, 4, 5, and 6 , FIG. 6 lists variousrelationships between hydrogen-exhaust gas heat exchangercharacteristics and operational and architectural characteristics of aturbofan engine. Notably, the turbofan engine 100 and thehydrogen-exhaust gas heat exchanger 200 are arranged so that thehydrogen-exhaust gas heat exchanger 200 has a load capacity factor LCF.The load capacity factor LCF is a dimensionless quantity that relates aheat transfer surface area density HTSAD associated with thehydrogen-exhaust gas heat exchanger 200 and a process conductanceparameter PCP.

As will be explained more fully below, the heat transfer surface areadensity HTSAD is a function of the structural architecture of thehydrogen-exhaust gas heat exchanger 200. The process conductanceparameter PCP is a measure of the flow potential of the process fluid,which in this instance is exhaust gas. The process conductance parameterPCP is a function of certain aspects of the hydrogen-exhaust gas heatexchanger 200, certain characteristics of hydrogen, conditionsassociated with the turbofan engine 100 at takeoff, and the architectureof the turbofan engine 100. Specifically, the process conductanceparameter PCP relates an exhaust gas temperature at takeoff T_(EG), anambient air temperature at takeoff T_(Amb), a critical temperature ofhydrogen T_(H2 Crit), an exhaust gas mass flowrate at takeoff {dot over(m)}_(EG), a mass flowrate factor of hydrogen at critical conditionm_(H2 Crit) a fan diameter D_(Fan) of the fan 134, and a number ofturbine stages of one or more turbines N_(Turb) of the turbofan engine100.

The load capacity factor LCF is defined as a product raised to aone-quarter power (or one-fourth power), wherein the product isdetermined by multiplying the heat transfer surface area density HTSADassociated with the hydrogen-exhaust gas heat exchanger 200 by theprocess conductance parameter PCP:LCF=(HTSAD*PCP)^(1/4)  (1)

The heat transfer surface area density HTSAD of (1) provides a measureof the compactness of the hydrogen-exhaust gas heat exchanger 200. Theheat transfer surface area density HTSAD is defined as a quotientdetermined by dividing a heat exchanger channel surface area A_(HT)associated with a plurality of channels 241, 242 of the hydrogen-exhaustgas heat exchanger 200 by a heat exchanger channel volume V_(HT)associated with the plurality of channels 241, 242. Stated differently,the heat exchanger channel surface area A_(HT) divided by the heatexchanger channel volume V_(HT) is equal to the heat transfer surfacearea density HTSAD. The heat exchanger channel surface area A_(HT) isdefined by a surface area of the channels 241, 242 of thehydrogen-exhaust gas heat exchanger 200. The heat exchanger channelvolume V_(HT) is defined by a volume of the channels 241, 242 of thehydrogen-exhaust gas heat exchanger 200. In this regard, the heattransfer surface area density HTSAD relates the surface area of thechannels 241, 242 with the volume of the channels 241, 242. The unit ofmeasure for the heat transfer surface area density HTSAD is meterssquared per meters cubed (m²/m³). The heat transfer surface area densityHTSAD is defined by the inventors as follows:HTSAD=A _(HT) /V _(HT)  (2)

The heat exchanger channel surface area A_(HT) may be determined asfollows. First, the surface area associated with each channel of eachcore of the hydrogen-exhaust gas heat exchanger 200 is determined. Thesurface area for a given one of the channels may be defined as acircumference C1 (see FIG. 5 depicting a circumference of one of thesecond channels 242) of the given channel multiplied by a length L1(FIG. 4 ) of the given channel. As will be appreciated, thecircumference C1 of the given channel may be defined as the diameter D1(see FIG. 5 depicting a diameter of one of the second channels 242) ofthe given channel multiplied by Pi (π). Second, once the surface areaassociated with each channel 241, 242 of the core 240 of each exchangerunit 210 of the hydrogen-exhaust gas heat exchanger 200 is determined,the surface area for each channel 241, 242 is summed to determine theheat exchanger channel surface area A_(HT). In this regard, the heatexchanger channel surface area A_(HT) describes the total surface areaassociated with the channels 241, 242 of the core 240 of each exchangerunit 210 of the hydrogen-exhaust gas heat exchanger 200.

The heat exchanger channel volume V_(HT) may be determined as follows.First, the volume associated with each channel of the core of eachexchanger unit 210 is determined. The volume for a given one of thechannels may be defined as an area A1 of the given channel (representedin FIG. 5 by the cross hatching in one of the first channels 241)multiplied by the length L1 of the given channel. As will beappreciated, the area A1 of the given channel may be defined as thediameter D1 squared multiplied by Pi (π) multiplied by one quarter, orstated differently, the radius of the given channel squared multipliedby Pi (π). Second, once the volume associated with each channel of thecore of each exchanger unit 210 of the hydrogen-exhaust gas heatexchanger 200 is determined, the volume for each channel is summed todetermine the heat exchanger channel volume V_(HT). In this regard, theheat exchanger channel volume V_(HT) describes the total volumeassociated with the channels 241, 242 of the core 240 of each exchangerunit 210 of the hydrogen-exhaust gas heat exchanger 200.

The process conductance parameter PCP of (1) is defined as a productdetermined by multiplying an absolute value of a first quotient by asecond quotient and by a third quotient. The first quotient isdetermined by dividing a first difference determined by subtracting theambient air temperature at takeoff T_(Amb) from the exhaust gastemperature at takeoff T_(EG) by a second difference determined bysubtracting the ambient air temperature at takeoff T_(Amb) from thecritical temperature of hydrogen T_(H2 Crit). The second quotient isdetermined by dividing the exhaust gas mass flowrate at takeoff {dotover (m)}_(EG) by the mass flowrate factor of hydrogen at criticalcondition m_(H2 Crit). The third quotient is determined by dividing thefan diameter D_(FAN) of the fan 134 by the number of turbine stages ofthe one or more turbines N_(Turb) of the turbofan engine 100. The unitof measure for the process conductance parameter PCP is meters (m). Theprocess conductance parameter PCP is defined by the inventors asfollows:

$\begin{matrix}{{P{CP}} = {{❘\frac{T_{EG} - T_{Amb}}{T_{H2{Crit}} - T_{Amb}}❘}*\left( {{\overset{˙}{m}}_{EG}/m_{H2{Crit}}} \right)*\left( {D_{Fan}/N_{Turb}} \right)}} & (3)\end{matrix}$

The ambient air temperature at takeoff T_(Amb) corresponds to anormalized ambient air temperature, which is taken as fifteen degreesCelsius (15° C.). The unit of measure of the ambient air temperature attakeoff T_(Amb) is degrees Celsius. The exhaust gas temperature attakeoff T_(EG) is a normalized temperature of the exhaust gas exhaustedfrom the exhaust section 126 at takeoff. The unit of measure of theexhaust gas temperature at takeoff T_(EG) is degrees Celsius. Thecritical temperature of hydrogen T_(H2 Crit) corresponds to aliquid-vapor critical temperature of hydrogen, which corresponds tonegative two hundred thirty-nine and ninety-five hundredths degreesCelsius (−239.95° C.). The unit of measure of the critical temperatureof hydrogen T_(H2 Crit) is degrees Celsius. The exhaust gas massflowrate at takeoff {dot over (m)}_(EG) corresponds to a mass flowratethrough the exhaust section 126 of the turbofan engine 100 at takeofftaken at a maximum takeoff thrust setting associated with the turbofanengine 100. The unit of measure of the exhaust gas mass flowrate attakeoff {dot over (m)}_(EG) is kilograms per second (kg/s).

The fan diameter D_(FAN) is defined as a distance spanning between aleading edge tip of one fan blade 136 to a leading edge tip of aradially opposite fan blade 136. Stated another way, the fan diameterD_(FAN) may be defined as a fan radius R_(FAN) multiplied by two, orstated mathematically, as D_(FAN)=R_(FAN)*2, wherein the fan radiusR_(FAN) spans from the longitudinal centerline 102 to a leading edge tipof one of the fan blades 136. In some example embodiments, the fandiameter D_(FAN) of the fan 134 of the turbofan engine 100 is between0.5 m and 3.5 m. In instances in which the fan section 104 includes aplurality of fan stages, the fan diameter D_(FAN) is to be determinedbased on the fan having the largest fan diameter.

The number of turbine stages N_(Turb) of the turbofan engine is definedas the number of stages of a turbine section of the turbofan engine. Theturbine section of a turbofan engine can include one or more turbines.As one example, a turbine section of a turbofan engine can include ahigh pressure turbine and a low pressure turbine. The high pressureturbine and the low pressure turbine can both include one or morestages. As another example, a turbine section of a turbofan engine caninclude a high pressure turbine, an intermediate pressure turbine, and alow pressure turbine. The high pressure turbine, the intermediatepressure turbine, and the low pressure turbine can all include one ormore stages. As used herein, a “turbine stage” is defined as an array ofairfoils that are mechanically coupled with a shaft of a turbofan engineand rotatable a longitudinal centerline of the turbofan engine.

By way of example, the number of turbine stages N_(Turb) of the turbofanengine 100 of FIG. 1 is seven (7). As shown, the turbine section 120includes two turbines, including the HP turbine 122 and the LP turbine124. The HP turbine 122 includes a first array of airfoils (the leadline of 166 is pointing to one airfoil of the first array in FIG. 1 )that are rotatable the longitudinal centerline 102. The airfoils of thefirst array are mechanically coupled with the HP shaft 128. The HPturbine 122 also includes a second array of airfoils that are rotatablethe longitudinal centerline 102. The second array of airfoils ispositioned aft of the first array along the axial direction A; an arrayof stator vanes is positioned between the first and second arrays alongthe axial direction A. The airfoils of the second array are mechanicallycoupled with the HP shaft 128. The rotating airfoils of the first andsecond arrays are labeled as HP turbine blades 166 in FIG. 1 .Accordingly, for this embodiment, the HP turbine 122 has two (2) stages.

The LP turbine 124 includes five (5) arrays of airfoils that arerotatable the longitudinal centerline 102. The rotating airfoils of thearrays of the LP turbine 124 are labeled as LP turbine blades 170 inFIG. 1 . An array of stator vanes is positioned between each adjacentpair of airfoils that are rotatable the longitudinal centerline 102. Thearrays of stator vanes are labeled as LP turbine stator vanes 168 inFIG. 1 . The five (5) arrays of airfoils that are rotatable thelongitudinal centerline 102 are mechanically coupled with the LP shaft130. Thus, the LP turbine 124 has five (5) stages. Accordingly, the HPturbine 122 has two (2) stages and the LP turbine 124 has five (5)stages, and thus, the turbine section 120 of the turbofan engine 100 ofFIG. 1 has seven (7) stages. In this regard, the number of turbinestages N_(Turb) of the turbofan engine 100 of FIG. 1 is equal to seven(7).

In some embodiments, the number of turbine stages N_(Turb) of theturbofan engine is between 2 and 10, including endpoints 2 and 10. Insome embodiments, the number of turbine stages N_(Turb) of the turbofanengine is between 5 and 10, including endpoints 5 and 10. In otherembodiments, the number of turbine stages N_(Turb) of the turbofanengine is between 7 and 10, including endpoints 7 and 10.

The mass flowrate factor of hydrogen at critical condition m_(H2 Crit)of (3) is defined as a product determined by multiplying a criticaldensity of hydrogen ρ_(H2 Crit) by a fourth quotient raised to a halfpower and by a cross-sectional area of a one inch inner diameter pipeA_(1″ Pipe ID). The fourth quotient is determined by dividing a productby the critical density of hydrogen ρ_(H2 Crit), wherein the product isdetermined by multiplying two by a third difference determined bysubtracting an ambient pressure at takeoff P_(Amb) from a criticalpressure of hydrogen P_(H2 Crit). The hydrogen at critical conditionm_(H2 Crit) is defined by the inventors as follows:

$\begin{matrix}{m_{H2{Crit}} = {\rho_{H2{Crit}}*\left( \frac{2*\left( {P_{H2{Crit}} - P_{Amb}} \right)}{\rho_{H2{Crit}}} \right)^{\frac{1}{2}}*A_{1^{''}{Pipe}{ID}}}} & (4)\end{matrix}$

The critical density of hydrogen ρ_(H2 Crit) corresponds to a density ofhydrogen at the critical point, or rather, the liquid-vapor point. Asused herein, the critical density of hydrogen corresponds to 31.36kg/m³. The unit of measure of the critical density of hydrogenρ_(H2 Crit) is kilograms per meters cubed (kg/m³). The critical pressureof hydrogen P_(H2 Crit) corresponds to a pressure of hydrogen at thecritical point, or rather, the liquid-vapor point. As used herein, thecritical pressure of hydrogen corresponds to 12.86 bars. The unit ofmeasure of the critical pressure of hydrogen P_(H2 Crit) is bars. Theambient pressure at takeoff P_(Amb), as used herein, corresponds to onebar (1 bar). The unit of measure of the ambient pressure at takeoffP_(Amb) is bars. The cross-sectional area of a one inch inner diameterpipe A_(1″ Pipe ID) corresponds to seventy-nine hundredths inchessquared (0.79 in²), or five and one tenth centimeters squared (5.1 cm²).The unit of measure of the cross-sectional area of a one inch innerdiameter pipe A_(1″ Pipe ID) is in inches squared.

In some embodiments, the load capacity factor LCF is between 4.37 and28.65 for the fan diameter D_(FAN) of the fan 134 being between 0.5 and3.5 meters and the heat transfer surface area density HTSAD beingbetween 500 m²/m³ and 10,000 m²/m³. FIG. 7 graphically depicts the loadcapacity factor LCF as a function of the fan diameter D_(FAN) for suchexample embodiments.

In yet other embodiments, the load capacity factor LCF is between 6.84and 28.65 for the fan diameter D_(FAN) of the fan 134 being between 0.5and 3.5 meters and the heat transfer surface area density HTSAD beingbetween 3,000 m²/m³ and 10,000 m²/m³. FIG. 8 graphically depicts theload capacity factor LCF as a function of the fan diameter D_(FAN) forsuch example embodiments.

In some further embodiments, the load capacity factor LCF is between4.37 and 21.20 for the fan diameter D_(FAN) of the fan 134 being between0.5 and 3.5 meters and the heat transfer surface area density HTSADbeing between 500 m²/m³ and 3,000 m²/m³. FIG. 9 graphically depicts theload capacity factor LCF as a function of the fan diameter D_(FAN) forsuch example embodiments.

In yet other embodiments, the load capacity factor LCF is between 6.84and 20.69 for the fan diameter D_(FAN) of the fan 134 being between 0.5and 2.0 meters and the heat transfer surface area density HTSAD beingbetween 3,000 m²/m³ and 10,000 m²/m³. FIG. 10 graphically depicts theload capacity factor LCF as a function of the fan diameter D_(FAN) forsuch example embodiments.

In some other embodiments, the load capacity factor LCF is between 15.31and 28.65 for the fan diameter D_(FAN) of the fan 134 being between 2.0and 3.5 meters and the heat transfer surface area density HTSAD beingbetween 3,000 m²/m³ and 10,000 m²/m³. FIG. 11 graphically depicts theload capacity factor LCF as a function of the fan diameter D_(FAN) forsuch example embodiments.

In yet further embodiments, the load capacity factor LCF is between 4.37and 15.31 for the fan diameter D_(FAN) of the fan 134 being between 0.5and 2.0 meters and the heat transfer surface area density HTSAD beingbetween 500 m²/m³ and 3,000 m²/m³. FIG. 12 graphically depicts the loadcapacity factor LCF as a function of the fan diameter D_(FAN) for suchexample embodiments.

In other embodiments, the load capacity factor LCF is between 9.78 and21.20 for the fan diameter D_(FAN) of the fan 134 being between 2.0 and3.5 meters and the heat transfer surface area density HTSAD beingbetween 500 m²/m³ and 3,000 m²/m³. FIG. 13 graphically depicts the loadcapacity factor LCF as a function of the fan diameter D_(FAN) for suchexample embodiments.

With reference now to FIG. 14 , a table is provided listing variousexamples.

EXAMPLE 1: In a first example, a turbofan engine includes ahydrogen-exhaust gas heat exchanger. The hydrogen-exhaust gas heatexchanger is arranged so that exhaust gas produced by the turbofanengine imparts thermal energy to hydrogen, e.g., being delivered forcombustion. The hydrogen-exhaust gas heat exchanger is further arrangedso that the heat transfer surface area density HTSAD associated with thehydrogen-exhaust gas heat exchanger is 600 m²/m³. Further, for the firstexample, the fan has a fan diameter D_(FAN) of 0.5 m. The turbofanengine has two (2) turbine stages. The exhaust gas temperature attakeoff T_(EG) is seven hundred twenty-five degrees Celsius (725° C.).The exhaust gas mass flowrate at takeoff {dot over (m)}_(EG) is eight(8) kilograms per second (kg/s). Accordingly, for the first example, theload capacity factor LCF is 5.26.

EXAMPLE 2: In a second example, a turbofan engine includes ahydrogen-exhaust gas heat exchanger. The hydrogen-exhaust gas heatexchanger is arranged so that exhaust gas produced by the turbofanengine imparts thermal energy to hydrogen, e.g., being delivered forcombustion. The hydrogen-exhaust gas heat exchanger is further arrangedso that the heat transfer surface area density HTSAD associated with thehydrogen-exhaust gas heat exchanger is 3,000 m²/m³. Further, for thesecond example, the fan has a fan diameter D_(FAN) of 2.0 m. Theturbofan engine has five (5) turbine stages. The exhaust gas temperatureat takeoff T_(EG) is nine hundred fifty degrees Celsius (950° C.). Theexhaust gas mass flowrate at takeoff {dot over (m)}_(EG) is ninety (90)kilograms per second (kg/s). Accordingly, for the second example, theload capacity factor LCF is 17.35.

EXAMPLE 3: In a third example, a turbofan engine includes ahydrogen-exhaust gas heat exchanger. The hydrogen-exhaust gas heatexchanger is arranged so that exhaust gas produced by the turbofanengine imparts thermal energy to hydrogen, e.g., being delivered forcombustion. The hydrogen-exhaust gas heat exchanger is further arrangedso that the heat transfer surface area density HTSAD associated with thehydrogen-exhaust gas heat exchanger is 10,000 m²/m³. Further, for thethird example, the fan has a fan diameter D_(FAN) of 3.5 m. The turbofanengine has ten (10) turbine stages. The exhaust gas temperature attakeoff T_(EG) is one thousand one hundred fifty degrees Celsius (1,150°C.). The exhaust gas mass flowrate at takeoff m_(EG) is one hundred(180) kilograms per second (kg/s). Accordingly, for the third example,the load capacity factor LCF is 28.30.

FIG. 15 provides a flow diagram for a method 300 of operating a turbofanengine having a hydrogen-exhaust gas heat exchanger. The turbofan enginecan be mounted to an aircraft, for example.

At 302, the method 300 includes operating a turbofan engine so that ahydrogen-exhaust gas heat exchanger of the turbofan engine processes,using exhaust gas produced by the turbofan engine, a heat duty ofhydrogen being delivered to a combustion section of the turbofan engine,the turbofan engine having one or more turbines and a fan, thehydrogen-exhaust gas heat exchanger defining a load capacity factorbeing determined by raising a product to a one-quarter power, theproduct being determined by multiplying a heat transfer surface areadensity associated with the hydrogen-exhaust gas heat exchanger by aprocess conductance parameter that relates an exhaust gas temperature attakeoff, an ambient air temperature at takeoff, a critical temperatureof hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowratefactor of hydrogen at critical condition, a fan diameter of the fan, anda number of turbine stages of the one or more turbines, and wherein theload capacity factor is between 4.37 and 28.65 for the fan diameter ofthe fan being between 0.5 and 3.5 meters and the heat transfer surfacearea density being between 500 m²/m³ and 10,000 m²/m³. The load capacityfactor according to such implementations is graphically represented inFIG. 7 .

In some implementations, the hydrogen-exhaust gas heat exchanger is oneof a plurality of heat exchangers that process the heat duty of hydrogenbeing delivered to the combustion section. For instance, in someimplementations, in operating the turbofan engine, a first heatexchanger upstream of the hydrogen-exhaust gas heat exchanger processesthe heat duty of hydrogen being delivered to the combustion section anda second heat exchanger downstream of the first heat exchanger andupstream of the hydrogen-exhaust gas heat exchanger processes the heatduty of hydrogen being delivered to the combustion section.

In some implementations, the turbofan engine includes a hydrogendelivery system for delivering hydrogen to the combustion section forcombustion. The hydrogen delivery system includes a hydrogen supply lineproviding flow communication between a hydrogen tank and the combustionsection. The hydrogen delivery system also includes a first heatexchanger positioned along the hydrogen supply line and arranged so thata first fluid imparts thermal energy to hydrogen flowing along thehydrogen supply line. The hydrogen delivery system further includes asecond heat exchanger positioned along the hydrogen supply linedownstream of the first heat exchanger, the second heat exchanger beingarranged so that a second fluid imparts thermal energy to hydrogenflowing along the hydrogen supply line. The hydrogen-exhaust gas heatexchanger is positioned along the hydrogen supply line downstream of thesecond heat exchanger and upstream of the combustion section. Thehydrogen-exhaust gas heat exchanger is arranged so that exhaust gas froman exhaust section of a core air flowpath defined a core turbine engineof the turbofan engine imparts thermal energy to hydrogen flowing alongthe hydrogen supply line.

In such implementations, in some instances, the first heat exchanger isa hydrogen-to-oil heat exchanger and the second heat exchanger is ahydrogen-to-air heat exchanger. Further, in such implementations, insome instances, the first heat exchanger, the second heat exchanger, andthe hydrogen-exhaust gas heat exchanger process the heat duty ofhydrogen flowing along the hydrogen supply line so that the hydrogendelivered to the combustion section is, or within a predetermined rangeof, a predetermined pre-combustion temperature. In some instances, thefirst heat exchanger processes between thirty and forty percent (30-40%)of the heat duty, the second heat exchanger processes between thirty andforty percent (30-40%) of the heat duty, and the hydrogen-exhaust gasheat exchanger processes between thirty and forty (30-40%) percent ofthe heat duty. In some instances, the hydrogen-exhaust gas heatexchanger processes a greatest percentage of the heat duty of thehydrogen flowing along the hydrogen supply line.

In some implementations, the hydrogen-exhaust gas heat exchangerincludes one or more exchanger units each having a core defining aplurality of channels. The heat transfer surface area density associatedwith the hydrogen-exhaust gas heat exchanger is defined as a quotientdetermined by dividing a heat exchanger channel surface area associatedwith the plurality of channels of the one or more exchanger units to aheat exchanger channel volume associated with the plurality of channelsof the one or more exchanger units.

In some implementations, the process conductance parameter is a productdetermined by multiplying an absolute value of a first quotient by asecond quotient and by a third quotient. The first quotient isdetermined by dividing a first difference determined by subtracting theambient air temperature at takeoff from the exhaust gas temperature attakeoff by a second difference determined by subtracting the ambient airtemperature at takeoff from the critical temperature of hydrogen. Thesecond quotient is determined by dividing the exhaust gas mass flowrateat takeoff by the mass flowrate factor of hydrogen at criticalcondition. The third quotient is determined by dividing the fan diameterof the fan by the number of turbine stages of the one or more turbines.

In some implementations, the mass flowrate factor of hydrogen atcritical condition is a product determined by multiplying a criticaldensity of hydrogen by a fourth quotient raised to a half power and by across-sectional area of a one inch inner diameter pipe. The fourthquotient is determined by dividing a product by the critical density ofhydrogen, the product being determined by multiplying two by a thirddifference determined by subtracting an ambient pressure at takeoff froma critical pressure of hydrogen.

In some implementations, the load capacity factor is between 6.84 and28.65 for the fan diameter of the fan being between 0.5 and 3.5 metersand the heat transfer surface area density being between 3,000 m²/m³ and10,000 m²/m³. The load capacity factor according to such implementationsis graphically represented in FIG. 8 .

In some other implementations, the load capacity factor is between 4.37and 21.20 for the fan diameter of the fan being between 0.5 and 3.5meters and the heat transfer surface area density being between 500m²/m³ and 3,000 m²/m³. The load capacity factor according to suchimplementations is graphically represented in FIG. 9 .

In yet other implementations, the load capacity factor is between 6.84and 20.69 for the fan diameter of the fan being between 0.5 and 2.0meters and the heat transfer surface area density being between 3,000m²/m³ and 10,000 m²/m³. The load capacity factor according to suchimplementations is graphically represented in FIG. 10 .

In further implementations, the load capacity factor is between 15.31and 28.65 for the fan diameter of the fan being between 2.0 and 3.5meters and the heat transfer surface area density being between 3,000m²/m³ and 10,000 m²/m³. The load capacity factor according to suchimplementations is graphically represented in FIG. 11 .

In some implementations, the load capacity factor is between 4.37 and15.31 for the fan diameter of the fan being between 0.5 and 2.0 metersand the heat transfer surface area density being between 500 m²/m³ and3,000 m²/m³. The load capacity factor according to such implementationsis graphically represented in FIG. 12 .

In yet other implementations, the load capacity factor is between 9.78and 21.20 for the fan diameter of the fan being between 2.0 and 3.5meters and the heat transfer surface area density being between 500m²/m³ and 3,000 m²/m³. The load capacity factor according to suchimplementations is graphically represented in FIG. 13 .

In some implementations, the number of turbine stages of the one or moreturbines is between two (2) and ten (10). In other implementations, thenumber of turbine stages of the one or more turbines is between five (5)and ten (10). In some implementations, the turbofan engine includes one(1) turbine. In some implementations, the turbofan engine includes two(2) turbines. In some other implementations, the turbofan engineincludes three (3) turbines.

Although specific features of various embodiments may be shown in somedrawings and not in others, this is for convenience only. In accordancewith the principles of the present disclosure, any feature of a drawingmay be referenced and/or claimed in combination with any feature of anyother drawing.

This written description uses examples to disclose the presentdisclosure, including the best mode, and also to enable any personskilled in the art to practice the disclosure, including making andusing any devices or systems and performing any incorporated methods.The patentable scope of the disclosure is defined by the claims, and mayinclude other examples that occur to those skilled in the art. Suchother examples are intended to be within the scope of the claims if theyinclude structural elements that do not differ from the literal languageof the claims, or if they include equivalent structural elements withinsubstantial differences from the literal languages of the claims.

Further aspects are provided by the subject matter of the followingclauses:

A turbofan engine, comprising: a core turbine engine defining a core airflowpath and having one or more turbines; a fan positioned upstream ofthe core turbine engine; and a hydrogen-exhaust gas heat exchanger inflow communication with an exhaust section of the core air flowpath, thehydrogen-exhaust gas heat exchanger defining a load capacity factorbeing determined by raising a product to a one-quarter power, theproduct being determined by multiplying a heat transfer surface areadensity associated with the hydrogen-exhaust gas heat exchanger by aprocess conductance parameter that relates an exhaust gas temperature attakeoff, an ambient air temperature at takeoff, a critical temperatureof hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowratefactor of hydrogen at critical condition, a fan diameter of the fan, anda number of turbine stages of the one or more turbines, and wherein theload capacity factor is between 4.37 and 28.65 for the fan diameter ofthe fan being between 0.5 and 3.5 meters and the heat transfer surfacearea density being between 500 m²/m³ and 10,000 m²/m³.

The turbofan engine of any preceding clause, further comprising: acombustion section; a hydrogen supply line providing flow communicationbetween a hydrogen tank and the combustion section; a first heatexchanger positioned along the hydrogen supply line and arranged so thata first fluid imparts thermal energy to hydrogen flowing along thehydrogen supply line; and a second heat exchanger positioned along thehydrogen supply line downstream of the first heat exchanger, the secondheat exchanger being arranged so that a second fluid imparts thermalenergy to hydrogen flowing along the hydrogen supply line, and whereinthe hydrogen-exhaust gas heat exchanger is positioned along the hydrogensupply line downstream of the second heat exchanger and upstream of thecombustion section, the hydrogen-exhaust gas heat exchanger beingarranged so that exhaust gas from the exhaust section of the core airflowpath imparts thermal energy to hydrogen flowing along the hydrogensupply line.

The turbofan engine of any preceding clause, wherein the first heatexchanger is a hydrogen-to-oil heat exchanger and the second heatexchanger is a hydrogen-to-air heat exchanger.

The turbofan engine of any preceding clause, wherein the first heatexchanger, the second heat exchanger, and the hydrogen-exhaust gas heatexchanger process a heat duty of hydrogen flowing along the hydrogensupply line so that hydrogen delivered to the combustion section is, orwithin a predetermined range of, a predetermined pre-combustiontemperature.

The turbofan engine of any preceding clause, wherein the first heatexchanger is configured to process between thirty and forty percent ofthe heat duty, the second heat exchanger is configured to processbetween twenty and forty percent of the heat duty, and thehydrogen-exhaust gas heat exchanger is configured to process betweenthirty and fifty percent of the heat duty.

The turbofan engine of any preceding clause, wherein thehydrogen-exhaust gas heat exchanger further comprises one or moreexchanger units each having a core defining a plurality of channels.

The turbofan engine of any preceding clause, wherein the heat transfersurface area density is defined as a quotient determined by dividing aheat exchanger channel surface area associated with the plurality ofchannels of the one or more exchanger units to a heat exchanger channelvolume associated with the plurality of channels of the one or moreexchanger units.

The turbofan engine of any preceding clause, wherein the processconductance parameter is a product determined by multiplying an absolutevalue of a first quotient by a second quotient and by a third quotient,the first quotient being determined by dividing a first differencedetermined by subtracting the ambient air temperature at takeoff fromthe exhaust gas temperature at takeoff by a second difference determinedby subtracting the ambient air temperature at takeoff from the criticaltemperature of hydrogen, the second quotient being determined bydividing the exhaust gas mass flowrate at takeoff by the mass flowratefactor of hydrogen at critical condition, and the third quotient beingdetermined by dividing the fan diameter of the fan by the number ofturbine stages of the one or more turbines.

The turbofan engine of any preceding clause, wherein the mass flowratefactor of hydrogen at critical condition is a product determined bymultiplying a critical density of hydrogen by a fourth quotient raisedto a half power and by a cross-sectional area of a one inch innerdiameter pipe, the fourth quotient being determined by dividing aproduct by the critical density of hydrogen, the product beingdetermined by multiplying two by a third difference determined bysubtracting an ambient pressure at takeoff from a critical pressure ofhydrogen.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 6.84 and 28.65 for the fan diameter of the fan beingbetween 0.5 and 3.5 meters and the heat transfer surface area densitybeing between 3,000 m²/m³ and 10,000 m²/m³.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 4.37 and 21.20 for the fan diameter of the fan beingbetween 0.5 and 3.5 meters and the heat transfer surface area densitybeing between 500 m²/m³ and 3,000 m²/m³.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 6.84 and 20.69 for the fan diameter of the fan beingbetween 0.5 and 2.0 meters and the heat transfer surface area densitybeing between 3,000 m²/m³ and 10,000 m²/m³.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 15.31 and 28.65 for the fan diameter of the fan beingbetween 2.0 and 3.5 meters and the heat transfer surface area densitybeing between 3,000 m²/m³ and 10,000 m²/m³.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 4.37 and 15.31 for the fan diameter of the fan beingbetween 0.5 and 2.0 meters and the heat transfer surface area densitybeing between 500 m²/m³ and 3,000 m²/m³.

The turbofan engine of any preceding clause, wherein the load capacityfactor is between 9.78 and 21.20 for the fan diameter of the fan beingbetween 2.0 and 3.5 meters and the heat transfer surface area densitybeing between 500 m²/m³ and 3,000 m²/m³.

The turbofan engine of any preceding clause, wherein the number ofturbine stages of the one or more turbines is between two and ten.

The turbofan engine of any preceding clause, wherein the number ofturbine stages of the one or more turbines is between five and ten.

A method, comprising: operating a turbofan engine so that ahydrogen-exhaust gas heat exchanger of the turbofan engine processes,using exhaust gas produced by the turbofan engine, a heat duty ofhydrogen being delivered to a combustion section of the turbofan engine,the turbofan engine having one or more turbines and a fan, thehydrogen-exhaust gas heat exchanger defining a load capacity factorbeing determined by raising a product to a one-quarter power, theproduct being determined by multiplying a heat transfer surface areadensity associated with the hydrogen-exhaust gas heat exchanger by aprocess conductance parameter that relates an exhaust gas temperature attakeoff, an ambient air temperature at takeoff, a critical temperatureof hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowratefactor of hydrogen at critical condition, a fan diameter of the fan, anda number of turbine stages of the one or more turbines, and wherein theload capacity factor is between 4.37 and 28.65 for the fan diameter ofthe fan being between 0.5 and 3.5 meters and the heat transfer surfacearea density being between 500 m²/m³ and 10,000 m²/m³.

The method of any preceding clause, wherein in operating the turbofanengine, a first heat exchanger upstream of the hydrogen-exhaust gas heatexchanger processes the heat duty of hydrogen being delivered to thecombustion section and a second heat exchanger downstream of the firstheat exchanger and upstream of the hydrogen-exhaust gas heat exchangerprocesses the heat duty of hydrogen being delivered to the combustionsection.

A hydrogen-exhaust gas heat exchanger in flow communication with anexhaust section of a turbofan engine, the hydrogen-exhaust gas heatexchanger comprising: one or more exchanger units each having a coredefining a plurality of channels, the hydrogen-exhaust gas heatexchanger defining a load capacity factor being determined by raising aproduct to a one-quarter power, the product being determined bymultiplying a heat transfer surface area density associated with thehydrogen-exhaust gas heat exchanger by a process conductance parameterthat relates an exhaust gas temperature of the turbofan engine attakeoff, an ambient air temperature at takeoff, a critical temperatureof hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowratefactor of hydrogen at critical condition, a fan diameter of a fan of theturbofan engine, and a number of turbine stages of one or more turbinesof the turbofan engine, and wherein the load capacity factor is between4.37 and 28.65 for the fan diameter of the fan being between 0.5 and 3.5meters and the heat transfer surface area density being between 500m²/m³ and 10,000 m²/m³.

We claim:
 1. A turbofan engine, comprising: a core turbine engine defining a core air flowpath and having one or more turbines; a fan positioned upstream of the core turbine engine; and a hydrogen-exhaust gas heat exchanger in flow communication with an exhaust section of the core air flowpath, the hydrogen-exhaust gas heat exchanger defining a load capacity factor being determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates an exhaust gas temperature at takeoff, an ambient air temperature at takeoff, a critical temperature of hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowrate factor of hydrogen at critical condition, a fan diameter of the fan, and a number of turbine stages of the one or more turbines, and wherein the load capacity factor is between 4.37 and 28.65 for the fan diameter of the fan being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m²/m³ and 10,000 m²/m³.
 2. The turbofan engine of claim 1, further comprising: a combustion section; a hydrogen supply line providing flow communication between a hydrogen tank and the combustion section; a first heat exchanger positioned along the hydrogen supply line and arranged so that a first fluid imparts thermal energy to hydrogen flowing along the hydrogen supply line; and a second heat exchanger positioned along the hydrogen supply line downstream of the first heat exchanger, the second heat exchanger being arranged so that a second fluid imparts thermal energy to hydrogen flowing along the hydrogen supply line, and wherein the hydrogen-exhaust gas heat exchanger is positioned along the hydrogen supply line downstream of the second heat exchanger and upstream of the combustion section, the hydrogen-exhaust gas heat exchanger being arranged so that exhaust gas from the exhaust section of the core air flowpath imparts thermal energy to hydrogen flowing along the hydrogen supply line.
 3. The turbofan engine of claim 2, wherein the first heat exchanger is a hydrogen-to-oil heat exchanger and the second heat exchanger is a hydrogen-to-air heat exchanger.
 4. The turbofan engine of claim 2, wherein the first heat exchanger, the second heat exchanger, and the hydrogen-exhaust gas heat exchanger process a heat duty of hydrogen flowing along the hydrogen supply line so that hydrogen delivered to the combustion section, is or within a predetermined range of, a predetermined pre-combustion temperature.
 5. The turbofan engine of claim 4, wherein the first heat exchanger is configured to process between thirty and forty percent of the heat duty, the second heat exchanger is configured to process between twenty and forty percent of the heat duty, and the hydrogen-exhaust gas heat exchanger is configured to process between thirty and fifty percent of the heat duty.
 6. The turbofan engine of claim 1, wherein the hydrogen-exhaust gas heat exchanger further comprises one or more exchanger units each having a core defining a plurality of channels.
 7. The turbofan engine of claim 6, wherein the heat transfer surface area density is defined as a quotient determined by dividing a heat exchanger channel surface area associated with the plurality of channels of the one or more exchanger units to a heat exchanger channel volume associated with the plurality of channels of the one or more exchanger units.
 8. The turbofan engine of claim 1, wherein the process conductance parameter is a product determined by multiplying an absolute value of a first quotient by a second quotient and by a third quotient, the first quotient being determined by dividing a first difference determined by subtracting the ambient air temperature at takeoff from the exhaust gas temperature at takeoff by a second difference determined by subtracting the ambient air temperature at takeoff from the critical temperature of hydrogen, the second quotient being determined by dividing the exhaust gas mass flowrate at takeoff by the mass flowrate factor of hydrogen at critical condition, and the third quotient being determined by dividing the fan diameter of the fan by the number of turbine stages of the one or more turbines.
 9. The turbofan engine of claim 8, wherein the mass flowrate factor of hydrogen at critical condition is a product determined by multiplying a critical density of hydrogen by a fourth quotient raised to a half power and by a cross-sectional area of a one inch inner diameter pipe, the fourth quotient being determined by dividing a product by the critical density of hydrogen, the product being determined by multiplying two by a third difference determined by subtracting an ambient pressure at takeoff from a critical pressure of hydrogen.
 10. The turbofan engine of claim 1, wherein the load capacity factor is between 6.84 and 28.65 for the fan diameter of the fan being between 0.5 and 3.5 meters and the heat transfer surface area density being between 3,000 m²/m³ and 10,000 m²/m³.
 11. The turbofan engine of claim 1, wherein the load capacity factor is between 4.37 and 21.20 for the fan diameter of the fan being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m²/m³ and 3,000 m²/m³.
 12. The turbofan engine of claim 1, wherein the load capacity factor is between 6.84 and 20.69 for the fan diameter of the fan being between 0.5 and 2.0 meters and the heat transfer surface area density being between 3,000 m²/m³ and 10,000 m²/m³.
 13. The turbofan engine of claim 1, wherein the load capacity factor is between 15.31 and 28.65 for the fan diameter of the fan being between 2.0 and 3.5 meters and the heat transfer surface area density being between 3,000 m²/m³ and 10,000 m²/m³.
 14. The turbofan engine of claim 1, wherein the load capacity factor is between 4.37 and 15.31 for the fan diameter of the fan being between 0.5 and 2.0 meters and the heat transfer surface area density being between 500 m²/m³ and 3,000 m²/m³.
 15. The turbofan engine of claim 1, wherein the load capacity factor is between 9.78 and 21.20 for the fan diameter of the fan being between 2.0 and 3.5 meters and the heat transfer surface area density being between 500 m²/m³ and 3,000 m²/m³.
 16. The turbofan engine of claim 1, wherein the number of turbine stages of the one or more turbines is between two and ten.
 17. The turbofan engine of claim 1, wherein the number of turbine stages of the one or more turbines is between five and ten.
 18. A method, comprising: operating a turbofan engine so that a hydrogen-exhaust gas heat exchanger of the turbofan engine processes, using exhaust gas produced by the turbofan engine, a heat duty of hydrogen being delivered to a combustion section of the turbofan engine, the turbofan engine having one or more turbines and a fan, the hydrogen-exhaust gas heat exchanger defining a load capacity factor being determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates an exhaust gas temperature at takeoff, an ambient air temperature at takeoff, a critical temperature of hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowrate factor of hydrogen at critical condition, a fan diameter of the fan, and a number of turbine stages of the one or more turbines, and wherein the load capacity factor is between 4.37 and 28.65 for the fan diameter of the fan being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m²/m³ and 10,000 m²/m³.
 19. The method of claim 18, wherein in operating the turbofan engine, a first heat exchanger upstream of the hydrogen-exhaust gas heat exchanger processes the heat duty of hydrogen being delivered to the combustion section and a second heat exchanger downstream of the first heat exchanger and upstream of the hydrogen-exhaust gas heat exchanger processes the heat duty of hydrogen being delivered to the combustion section.
 20. A hydrogen-exhaust gas heat exchanger in flow communication with an exhaust section of a turbofan engine, the hydrogen-exhaust gas heat exchanger comprising: one or more exchanger units each having a core defining a plurality of channels, the hydrogen-exhaust gas heat exchanger defining a load capacity factor being determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates an exhaust gas temperature of the turbofan engine at takeoff, an ambient air temperature at takeoff, a critical temperature of hydrogen, an exhaust gas mass flowrate at takeoff, a mass flowrate factor of hydrogen at critical condition, a fan diameter of a fan of the turbofan engine, and a number of turbine stages of one or more turbines of the turbofan engine, and wherein the load capacity factor is between 4.37 and 28.65 for the fan diameter of the fan being between 0.5 and 3.5 meters and the heat transfer surface area density being between 500 m²/m³ and 10,000 m²/m³. 